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Research Papers: Gas Turbines: Turbomachinery

The Blade Profile Orientations Effects on the Aeromechanics of Multirow Turbomachines

[+] Author and Article Information
M. T. Rahmati

Department of Engineering Science,
Oxford University,
Parks Road,
Oxford OX1 3PJ, UK
e-mail: mt.rahmati@brunel.ac.uk

L. He

Department of Engineering Science,
Oxford University,
Parks Road,
Oxford OX1 3PJ, UK

Y. S. Li

Siemens Industrial
Turbomachinery (SIT),
Lincoln LN5 7FD, England

1Present address: Department of Mechanical, Aerospace, and Civil Engineering, Brunel University London, Uxbridge UB8 3PH, UK.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received April 12, 2015; final manuscript received May 3, 2015; published online November 25, 2015. Editor: David Wisler.

J. Eng. Gas Turbines Power 138(6), 062606 (Nov 25, 2015) (9 pages) Paper No: GTP-15-1128; doi: 10.1115/1.4030569 History: Received April 12, 2015

The aerodynamic damping calculations for turbomachinery blade aeromechanics applications are typically carried out in an isolated blade row. The aerodynamic damping of vibrating blades, however, can be significantly influenced by the presence of neighboring blade rows. A highly efficient frequency-domain method is used to investigate the multirow effects on the blade row aerodynamic damping of a compressor and turbine. Depending on the blade profile orientations, the flow reflection effects from adjacent blade rows can significantly alter both unsteady pressure amplitudes and phase angles. Therefore, the blade aerodamping might increase or decrease depending on the stabilizing or destabilizing effects of the unsteady pressure changes. In the case of the compressor, the downstream stator significantly changes the unsteady pressure distribution on the rotor thus, affects the rotor aerodamping. In the turbine case, the upstream stator has a major effect on the aerodamping, while the downstream stator does not significantly change the rotor aerodamping.

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References

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Figures

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Fig. 1

Multipassage computational domain (time-domain method)

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Fig. 2

Single passage computational domain

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Fig. 3

Sliding plane interface between a rotor domain and a stator domain

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Fig. 4

Vibrating rotor of a frontal compressor stage

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Fig. 5

Vibrating rotor of a rear turbine stage

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Fig. 6

Computational mesh for DLR compressor stage

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Fig. 7

Nonbeating vibration and blade passing frequencies

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Fig. 8

Vibration component compressed during the time trace reconstruction

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Fig. 9

Vibration component drastically compressed during the time trace reconstruction

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Fig. 10

Local worksum distributions on pressure side (“+” destabilizing, “−” stabilizing)

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Fig. 11

Local worksum distributions on suction side (+ destabilizing, − stabilizing)

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Fig. 12

Computational mesh (at midspan) for the turbine stage

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Fig. 13

Amplitude of first harmonic unsteady pressure at midspan (PT2)

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Fig. 14

Phase angle of first harmonic unsteady pressure at midspan (PT2)

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Fig. 15

Local worksum distributions on pressure side (PT2)

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Fig. 16

Local worksum distributions on suction side (PT2)

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Fig. 17

Local worksum distributions on pressure side (reflection effects from downstream row included)

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Fig. 18

Local worksum distributions on pressure side (reflection effects from upstream row included)

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Fig. 19

Local worksum distributions on pressure side (reflection effects from both downstream and upstream rows included)

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Fig. 20

Local worksum distributions on suction side (reflection effects from downstream row included)

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Fig. 21

Local worksum distributions on suction side (reflection effects from upstream row included)

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Fig. 22

Local worksum distributions on suction side (reflection effects from both downstream and upstream rows included)

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